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GOE 776 AIRFOIL (goe776-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 776 AIRFOIL (goe776-il)
Reynolds number: 100,000
Max Cl/Cd: 33.33 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe776-il-100000.txt
Download as CSV file: xf-goe776-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 776 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.4013   0.14311   0.13613  -0.0308   1.0000   0.2446
 -13.500  -0.9512   0.05841   0.05050  -0.0541   1.0000   0.2423
 -13.250  -1.0704   0.04984   0.04144  -0.0464   1.0000   0.2440
 -13.000  -1.0027   0.05154   0.04344  -0.0487   1.0000   0.2493
 -12.750  -0.9967   0.05061   0.04254  -0.0469   1.0000   0.2536
 -12.500  -1.0447   0.04727   0.03901  -0.0407   1.0000   0.2568
 -12.250  -1.0963   0.04467   0.03620  -0.0326   1.0000   0.2594
 -12.000  -1.1501   0.04290   0.03420  -0.0225   1.0000   0.2614
 -11.750  -1.0782   0.04344   0.03510  -0.0279   1.0000   0.2680
 -11.500  -1.0948   0.04254   0.03418  -0.0222   1.0000   0.2717
 -11.250  -1.1323   0.04146   0.03298  -0.0133   1.0000   0.2746
 -11.000  -1.1772   0.04056   0.03192  -0.0028   1.0000   0.2769
 -10.750  -1.1904   0.03968   0.03099   0.0030   1.0000   0.2806
 -10.500  -1.1615   0.03969   0.03122   0.0029   1.0000   0.2860
 -10.250  -1.1735   0.03910   0.03060   0.0086   1.0000   0.2902
 -10.000  -1.1970   0.03820   0.02953   0.0159   1.0000   0.2944
  -9.750  -1.1998   0.03747   0.02877   0.0201   1.0000   0.2990
  -9.500  -1.1819   0.03740   0.02887   0.0215   1.0000   0.3043
  -9.250  -1.1861   0.03687   0.02829   0.0259   1.0000   0.3095
  -9.000  -1.2024   0.03599   0.02716   0.0321   1.0000   0.3147
  -8.750  -1.1824   0.03580   0.02718   0.0329   1.0000   0.3201
  -8.500  -1.1571   0.03557   0.02699   0.0324   0.9962   0.3276
  -8.250  -1.1242   0.03494   0.02622   0.0301   0.9883   0.3365
  -8.000  -1.0784   0.03496   0.02641   0.0264   0.9804   0.3450
  -7.750  -1.0532   0.03427   0.02548   0.0254   0.9710   0.3545
  -7.500  -1.0037   0.03432   0.02579   0.0213   0.9634   0.3628
  -7.250  -0.9791   0.03378   0.02506   0.0208   0.9532   0.3725
  -7.000  -0.9330   0.03363   0.02510   0.0172   0.9452   0.3809
  -6.750  -0.9025   0.03328   0.02469   0.0160   0.9358   0.3908
  -6.500  -0.8658   0.03292   0.02439   0.0141   0.9262   0.3996
  -6.250  -0.8169   0.03268   0.02417   0.0099   0.9208   0.4107
  -6.000  -0.8025   0.03224   0.02370   0.0119   0.9070   0.4186
  -5.750  -0.7490   0.03208   0.02367   0.0073   0.9016   0.4292
  -5.500  -0.7405   0.03162   0.02306   0.0102   0.8880   0.4380
  -5.250  -0.6846   0.03148   0.02313   0.0055   0.8821   0.4479
  -5.000  -0.6680   0.03101   0.02247   0.0071   0.8714   0.4583
  -4.750  -0.6207   0.03085   0.02255   0.0039   0.8631   0.4671
  -4.500  -0.5785   0.03019   0.02176   0.0013   0.8578   0.4797
  -4.250  -0.5462   0.03012   0.02187   0.0008   0.8469   0.4875
  -4.000  -0.5116   0.02968   0.02140  -0.0002   0.8386   0.4986
  -3.750  -0.4589   0.02908   0.02088  -0.0040   0.8341   0.5091
  -3.500  -0.4433   0.02905   0.02088  -0.0017   0.8207   0.5182
  -3.250  -0.4053   0.02842   0.02023  -0.0030   0.8136   0.5290
  -3.000  -0.3530   0.02790   0.01977  -0.0065   0.8091   0.5401
  -2.750  -0.3509   0.02779   0.01960  -0.0020   0.7935   0.5495
  -2.500  -0.2973   0.02736   0.01929  -0.0055   0.7878   0.5596
  -2.250  -0.2933   0.02717   0.01898  -0.0014   0.7741   0.5708
  -2.000  -0.2425   0.02685   0.01882  -0.0044   0.7663   0.5800
  -1.750  -0.2206   0.02653   0.01842  -0.0030   0.7564   0.5919
  -1.500  -0.1883   0.02640   0.01838  -0.0032   0.7448   0.6011
  -1.250  -0.1489   0.02593   0.01784  -0.0043   0.7380   0.6133
  -1.000  -0.1343   0.02603   0.01801  -0.0018   0.7233   0.6228
  -0.750  -0.0924   0.02574   0.01770  -0.0033   0.7152   0.6341
  -0.500  -0.0801   0.02575   0.01773  -0.0005   0.7017   0.6450
  -0.250  -0.0375   0.02564   0.01763  -0.0021   0.6925   0.6553
   0.000  -0.0254   0.02559   0.01756   0.0007   0.6802   0.6677
   0.250   0.0165   0.02564   0.01765  -0.0008   0.6699   0.6770
   0.500   0.0301   0.02554   0.01749   0.0018   0.6591   0.6906
   0.750   0.0703   0.02577   0.01777   0.0006   0.6475   0.6990
   1.000   0.0872   0.02559   0.01749   0.0027   0.6382   0.7136
   1.250   0.1239   0.02600   0.01801   0.0020   0.6255   0.7210
   1.500   0.1564   0.02597   0.01786   0.0018   0.6168   0.7336
   1.750   0.1781   0.02634   0.01834   0.0032   0.6042   0.7430
   2.000   0.2229   0.02650   0.01837   0.0012   0.5951   0.7526
   2.250   0.2331   0.02675   0.01872   0.0044   0.5834   0.7649
   2.500   0.2814   0.02710   0.01897   0.0018   0.5734   0.7722
   2.750   0.2892   0.02721   0.01913   0.0053   0.5634   0.7866
   3.000   0.3374   0.02771   0.01959   0.0027   0.5524   0.7923
   3.250   0.3632   0.02805   0.01992   0.0034   0.5428   0.8035
   3.500   0.3921   0.02835   0.02021   0.0037   0.5321   0.8127
   3.750   0.4409   0.02889   0.02066   0.0006   0.5221   0.8187
   4.000   0.4468   0.02900   0.02084   0.0045   0.5126   0.8335
   4.250   0.5099   0.02943   0.02105  -0.0009   0.5027   0.8372
   4.500   0.5383   0.03009   0.02187  -0.0010   0.4908   0.8452
   4.750   0.5655   0.03004   0.02167  -0.0006   0.4829   0.8573
   5.000   0.6108   0.03077   0.02249  -0.0037   0.4708   0.8621
   5.250   0.6586   0.03094   0.02249  -0.0070   0.4611   0.8698
   5.500   0.6766   0.03135   0.02298  -0.0055   0.4519   0.8812
   5.750   0.7273   0.03160   0.02314  -0.0095   0.4411   0.8872
   6.000   0.7433   0.03190   0.02342  -0.0077   0.4334   0.9007
   6.250   0.7904   0.03226   0.02380  -0.0114   0.4219   0.9062
   6.500   0.8279   0.03253   0.02395  -0.0132   0.4132   0.9160
   6.750   0.8554   0.03293   0.02446  -0.0138   0.4030   0.9254
   7.000   0.9062   0.03302   0.02431  -0.0180   0.3942   0.9329
   7.250   0.9244   0.03360   0.02511  -0.0172   0.3845   0.9442
   7.500   0.9741   0.03359   0.02488  -0.0213   0.3757   0.9517
   7.750   0.9974   0.03423   0.02569  -0.0216   0.3664   0.9623
   8.000   1.0412   0.03428   0.02563  -0.0250   0.3574   0.9704
   8.250   1.0745   0.03479   0.02619  -0.0270   0.3487   0.9792
   8.500   1.1135   0.03500   0.02639  -0.0299   0.3396   0.9877
   8.750   1.1558   0.03530   0.02663  -0.0334   0.3312   0.9949
   9.000   1.1774   0.03580   0.02724  -0.0336   0.3231   1.0000
   9.250   1.1950   0.03585   0.02711  -0.0324   0.3175   1.0000
   9.500   1.1926   0.03655   0.02789  -0.0283   0.3123   1.0000
   9.750   1.1815   0.03728   0.02875  -0.0229   0.3071   1.0000
  10.000   1.1866   0.03757   0.02899  -0.0197   0.3019   1.0000
  10.250   1.2110   0.03777   0.02897  -0.0194   0.2966   1.0000
  10.500   1.1825   0.03878   0.03022  -0.0113   0.2927   1.0000
  10.750   1.1627   0.03955   0.03109  -0.0045   0.2886   1.0000
  11.000   1.1629   0.03989   0.03138  -0.0005   0.2841   1.0000
  11.250   1.1959   0.04011   0.03136  -0.0014   0.2786   1.0000
  11.500   1.1514   0.04107   0.03252   0.0092   0.2763   1.0000
  11.750   1.1080   0.04212   0.03370   0.0191   0.2738   1.0000
  12.000   1.0784   0.04327   0.03494   0.0265   0.2704   1.0000
  12.250   1.0875   0.04361   0.03520   0.0290   0.2659   1.0000
  12.500   1.1203   0.04385   0.03527   0.0285   0.2609   1.0000
  12.750   1.0664   0.04619   0.03784   0.0376   0.2585   1.0000
  13.000   1.0138   0.04945   0.04131   0.0446   0.2555   1.0000
  13.250   0.9795   0.05260   0.04459   0.0489   0.2518   1.0000
  13.500   1.1021   0.04826   0.03971   0.0427   0.2452   1.0000
  13.750   1.0181   0.05359   0.04543   0.0506   0.2433   1.0000
  14.000   0.3230   0.15053   0.14364   0.0250   0.2687   1.0000
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